Air supply system and air supply control method for pneumatic ejection of unmanned aerial vehicle

Abstract

The present invention belongs to the technical field of pneumatic ejection of unmanned aerial vehicles, and discloses an air supply system and air supply control method for pneumatic ejection of unmanned aerial vehicles, including: a high-pressure tank for supplying air to a low-pressure tank; a low-pressure tank connected to a plurality of launch tubes for providing an air source required for pneumatic ejection of unmanned aerial vehicles; a first air circuit control unit, including a pressure reducing valve and a switch solenoid valve arranged on a main pipeline; a second air circuit control unit, including a first pilot valve and a second pilot valve connected in series; a main control unit, which is respectively connected to a first pressure sensor and a switch solenoid valve, and is used to switch and control the switch solenoid valve according to the pressure data obtained from the first pressure sensor. The present invention adopts a two-stage pilot valve and a pressure reducing valve to form an air circuit control unit, and combines a closed-loop control unit formed by a solenoid valve, a main control unit and a pressure sensor to realize automatic air supply and air replenishment during continuous and rapid launch of unmanned aerial vehicles, and the air replenishment accuracy is high.

Description

Technical Field

[0001] The present invention belongs to the technical field of pneumatic ejection of unmanned aerial vehicles, and in particular relates to an air supply system and an air supply control method for pneumatic ejection of unmanned aerial vehicles. Background Art

[0002] With the rapid development of micro-UAVs and cruise missiles, swarm system combat methods have received more and more attention. Pneumatic ejection technology is to control the instantaneous deflation of the low-pressure air storage chamber through the pneumatic components of the ejection device, forming a high-pressure airflow in the launch tube, so that the UAV or cruise missile can reach the required exit speed, and realize the launch operation of the UAV and cruise missile. Existing pneumatic ejection devices are usually single-tube launch and do not have the ability to launch continuously; and cluster pneumatic ejection devices usually have a slow air replenishment speed, which is difficult to meet the needs of rapid and continuous launch.

[0003] In order to solve the problem of slow air replenishment during the continuous and rapid launch of drones, the cluster pneumatic ejection device uses a combination of high-pressure tanks and low-pressure tanks. The high-pressure tank automatically replenishes air into the low-pressure tank, and the air source in the low-pressure tank is used to eject the drone. Due to the large number of launch tubes and the large total air volume required for launch, the air pressure in the high-pressure tank is high, and the air pressure difference between the high-pressure tank and the low-pressure tank is large. When automatically replenishing air into the low-pressure tank, there is an overcharging problem, which makes it difficult to ensure the ejection pressure control accuracy during the continuous launch of drones. Summary of the invention

[0004] The object of the present invention is to provide an air supply system and an air supply control method for a pneumatic ejection of a UAV, so as to solve the problem that the ejection pressure control accuracy is low during the continuous launching of UAVs in the existing cluster pneumatic ejection device.

[0005] The present invention is achieved through the following technical solutions:

[0006] UAV pneumatic ejection air supply system, including:

[0007] The high-pressure tank is used to supply gas to the low-pressure tank, and the gas pressure in the high-pressure tank is greater than the gas pressure in the low-pressure tank;

[0008] A low-pressure tank, which is connected to a plurality of launch tubes and is used to provide an air source required for pneumatic ejection of the drone. The low-pressure tank is connected to the high-pressure tank through a main pipeline, and a first pressure sensor for detecting the air pressure of the low-pressure tank is provided on the low-pressure tank;

[0009] A first gas circuit control unit, comprising a pressure reducing valve and a switch solenoid valve arranged on the main pipe, wherein the front end of the inlet of the pressure reducing valve is connected to the high-pressure tank, the outlet end of the pressure reducing valve is connected to the switch solenoid valve, and the switch solenoid valve is connected to the low-pressure tank;

[0010] A second gas circuit control unit comprises a first pilot valve and a second pilot valve connected in series, wherein an inlet end of the first pilot valve is respectively connected to the inlet front end of the high-pressure tank and the pressure reducing valve, and an outlet end of the second pilot valve is connected to the pressure reducing valve, a set pressure value of the first pilot valve is greater than a target air pressure of the low-pressure tank, and a set pressure value of the second pilot valve is not less than the target air pressure of the low-pressure tank and less than a set pressure value of the first pilot valve;

[0011] A main control unit is connected to the first pressure sensor and the switch solenoid valve respectively, and is used to control the switch solenoid valve on and off according to the pressure data obtained from the first pressure sensor.

[0012] In some embodiments, the set pressure value of the first pilot valve is 2.5-3 times the target air pressure of the low-pressure tank.

[0013] In some embodiments, the set pressure value of the second pilot valve is 1.5-2 times the target air pressure of the low-pressure tank.

[0014] In some embodiments, the low-pressure tank is provided with a first exhaust safety valve for pressure relief.

[0015] In some embodiments, an integrated valve block is provided on the main line, a first ball valve is provided between the first inlet end of the integrated valve block and the outlet end of the high-pressure tank, the outlet of the integrated valve block is respectively connected to the inlet end of the first pilot valve and the inlet front end of the pressure reducing valve, and a second pressure sensor for detecting the air pressure of the high-pressure tank and a second exhaust safety valve for pressure relief are provided on the integrated valve block.

[0016] In some embodiments, the second inlet end of the integrated valve block is provided with a quick-change connector for connecting to the base station air source, the outlet end of the integrated valve block is connected to the second ball valve, and the second ball valve is respectively connected to the inlet end of the first pilot valve and the inlet front end of the pressure reducing valve.

[0017] In some embodiments, a launch valve is provided between the low-pressure tank and each launch tube, and the launch valve is connected to the main control unit.

[0018] On the other hand, the present invention also provides an air supply control method based on the UAV pneumatic ejection air supply system, comprising:

[0019] The set pressure values ​​of the first pilot valve and the second pilot valve are set so that the set pressure value of the first pilot valve is greater than the air pressure required by the low-pressure tank, and the set pressure value of the second pilot valve is greater than the air pressure required by the low-pressure tank and less than the set pressure value of the first pilot valve, and the output pressure of the pressure reducing valve is controlled by the pressure output by the second pilot valve;

[0020] The main control unit controls the switch of the switch solenoid valve according to the pressure data obtained from the first pressure sensor. When the pressure data of the first pressure sensor reaches the target air pressure required by the low-pressure tank, the main control unit controls the switch solenoid valve to close.

[0021] In some embodiments, the air supply buffer zone is set, the minimum value of the air supply buffer zone is not less than the minimum value of the target air pressure value control accuracy range and the maximum value of the air supply buffer zone is greater than the maximum value of the target air pressure value control accuracy range;

[0022] When the pressure data detected by the first pressure sensor is within the air supply compensation buffer zone, the main control unit controls the switch solenoid valve to close.

[0023] In some embodiments, when the air pressure in the low-pressure tank reaches the target air pressure, the main control unit controls the launch valve of one of the launch tubes to be launched to open;

[0024] After completing the launch of a UAV, the main control unit controls the replenishment of air to the low-pressure tank until the target air pressure is reached, and the cycle is repeated in sequence to complete the launch of each launch tube.

[0025] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0026] The present invention adopts a two-stage pilot valve and a pressure reducing valve to form an air circuit control unit. The first pilot valve is used for filtering, and the second pilot valve controls the output pressure of the pressure reducing valve. The coordinated use of the two-stage pilot valve effectively reduces the problem that the set pressure value of the pilot valve will continue to increase during the continuous launch and air replenishment operation, and the output pressure of the pressure reducing valve cannot be effectively controlled. The output pressure of the pressure reducing valve can always be maintained within a constant range. Combined with the closed-loop control formed by the solenoid valve, the main control unit and the pressure sensor, automatic air supply and air replenishment during the continuous and rapid launch of the UAV is realized, and the air replenishment accuracy is high, which ensures the ejection pressure control accuracy during the continuous launch of the UAV.

[0027] The invention takes a short time to replenish the low-pressure tank with gas after each launch, has a high degree of automation, and satisfies the needs of continuous and rapid launch of the UAV well. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0029] Figure 1 The figure is a schematic diagram of the structure of the air supply system for pneumatic ejection of a UAV according to an embodiment of the present invention.

[0030] Figure 2 It is a curve chart of the air replenishment test performance of the pneumatic ejection air supply system of the UAV according to an embodiment of the present invention.

[0031] in:

[0032] 1. High-pressure tank, 2. Low-pressure tank, 3. Pressure reducing valve, 4. Switch solenoid valve, 5. First pilot valve, 6. Second pilot valve, 7. Main line, 8. Main control unit, 9. First pressure sensor, 10. Second pressure sensor, 11. First exhaust safety valve, 12. Second exhaust safety valve, 13. Integrated valve block, 14. First ball valve, 15. Second ball valve, 16. Quick-change connector, 17. Base station gas source, 18. Launch tube, 19. Launch valve. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0034] The commonly used air supply methods for pneumatic ejection include:

[0035] 1. Each launch tube is equipped with a high-pressure gas cylinder for independent gas supply. Since the volume of the gas cylinder is often small, the launch pressure is high and the overload is large. In addition, each gas cylinder needs to be inflated before launch, the launch preparation cycle is long, and the system control is complex.

[0036] Second, a compressor is set up to supply the total air source to achieve automatic air replenishment. However, due to the limitation of the compressor power, the air replenishment time is long and the air replenishment accuracy is difficult to guarantee.

[0037] 3. Automatic air replenishment is achieved by setting up a high-pressure tank to replenish air into the low-pressure tank, and controlling the opening and closing of the solenoid valve through a feedback signal. However, due to the large number of launch tubes, the total amount of air required is large, the total pressure in the high-pressure tank is high, and the pressure difference between the high-pressure tank and the low-pressure tank is large. Especially when replenishing air for the first few rounds, the problem of overcharging pressure is prone to occur, and the control accuracy of each ejection pressure cannot be guaranteed.

[0038] Fourth, a high-pressure tank is set up to replenish air into the low-pressure tank, and a mechanical pressure reducing valve and a solenoid valve are set in series in the air circuit control to control the air replenishment. This air supply control method will cause pressure pulses in the air pressure circuit during rapid and continuous ejection. The set pressure of the mechanical pressure reducing valve will gradually increase due to the pressure pulses generated, and it is also difficult to ensure the control accuracy of each ejection pressure.

[0039] In view of the problems existing in the existing air supply method for achieving continuous launch of pneumatic catapults, the present invention proposes an air supply system for pneumatic catapult launch of unmanned aerial vehicles. The air supply system adopts a method of automatically supplying and replenishing air from a high-pressure tank to a low-pressure tank, which can realize the rapid and continuous launch of multiple unmanned aerial vehicles, and the air source in the high-pressure tank can meet the launch of all sorties of unmanned aerial vehicles. The launch control operation is simple and the time required for launch preparation is short.

[0040] A two-stage pilot valve and a pressure reducing valve are combined to form an air circuit control unit, and are connected in series with a switch solenoid valve. Combined with the adopted closed-loop control method, the pressure fluctuation of the pressure reducing valve is controlled through the filtering and pressure control of the two-stage pilot valve, thereby realizing automatic and precise air supply and air replenishment operations for the low-pressure tank during continuous launching. The ejection pressure of each UAV can be accurately controlled to ensure that the ejection speed of the UAV out of the tube can be controlled within a stable range.

[0041] In some embodiments, the air supply system for the pneumatic ejection of the drone, referring to Figure 1 ,include:

[0042] The high-pressure tank 1 is used to supply gas to the low-pressure tank and to replenish gas in the low-pressure tank after each launch of the drone. The gas pressure in the high-pressure tank is greater than the gas pressure in the low-pressure tank. The gas source in the high-pressure tank can meet the launch requirements of all sorties in the launch system. After the high-pressure tank is inflated once, the launch requirements can be met, and the time required for launch preparation is short. Generally, the gas pressure in the high-pressure tank is 20-28 bar, and the gas pressure in the low-pressure tank is 2.0-2.6 bar. The gas pressure in the low-pressure tank can be set according to the launch requirements.

[0043] The low-pressure tank 2 is connected to a plurality of launch tubes and is used to provide the air source required for the pneumatic ejection of the UAV, thereby realizing the pneumatic ejection of the UAV; the low-pressure tank 2 is connected to the high-pressure tank 1 through a main pipe 7, and the high-pressure tank supplies and replenishes air to the low-pressure tank through the main pipe. A first pressure sensor 9 for detecting the air pressure of the low-pressure tank is provided on the low-pressure tank 2.

[0044] The first gas circuit control unit comprises a pressure reducing valve 3 and a switch solenoid valve 4 arranged on the main pipe, the inlet front end of the pressure reducing valve 3 is connected to the high-pressure tank 1, the outlet end of the pressure reducing valve 3 is connected to the switch solenoid valve 4, and the switch solenoid valve 4 is connected to the low-pressure tank 2;

[0045] The second air circuit control unit includes a first pilot valve 5 and a second pilot valve 6 connected in series, wherein the inlet end of the first pilot valve 5 is connected to the inlet front end of the high-pressure tank 1 and the pressure reducing valve 3 respectively, and the outlet end of the second pilot valve 6 is connected to the pressure reducing valve 3; wherein the set pressure value of the first pilot valve 5 is greater than the target air pressure of the low-pressure tank, and the set pressure value of the second pilot valve 6 is not less than the target air pressure of the low-pressure tank and less than the set pressure value of the first pilot valve.

[0046] The first gas path control unit and the second gas path control unit together constitute the gas path control unit of the gas supply system, realizing pressure control in gas supply and gas replenishment operations.

[0047] And a main control unit 8, which is connected to the first pressure sensor 9 and the switch solenoid valve 4 respectively, and is used to control the switch solenoid valve on and off according to the pressure data obtained from the first pressure sensor.

[0048] The main control unit serves as an automated control unit for the gas supply system and may use an existing controller. The controller can control the opening and closing of the switch solenoid valve according to the set control program by obtaining the pressure data in the low-pressure tank. When the gas pressure in the low-pressure tank is lower than the target pressure, the switch solenoid valve is controlled to open, so that the high-pressure tank can supply and replenish gas to the low-pressure tank. When the gas pressure in the low-pressure tank reaches the set target pressure, the switch solenoid valve is controlled to close, thereby realizing automated control of gas supply and replenishment.

[0049] During the process of supplying and replenishing air, the air supply system uses a first pilot valve and a second pilot valve to form a two-stage pilot valve, which is connected in series with the pressure reducing valve.

[0050] The set pressure value of the first pilot valve 5 is usually set to be much larger than the target pressure required by the low-pressure tank, for example, the set pressure value of the first pilot valve is set to be 2.5-3 times the target pressure of the low-pressure tank. The first pilot valve plays a filtering role in the gas circuit, which can reduce the pressure pulse generated during the continuous gas supply and gas replenishment process, thereby avoiding the problem of overcharging caused by the pressure pulse causing the pressure at the output end of the pressure reducing valve to gradually increase.

[0051] The set pressure value of the second pilot valve 6 is set to be slightly higher than the target pressure required by the low-pressure tank, for example, the set pressure value of the second pilot valve is set to be 1.5-2 times the target air pressure of the low-pressure tank; at this time, the pressure output by the second pilot valve is fed back to the pressure reducing valve, thereby controlling the output pressure of the pressure reducing valve on the main pipeline, realizing the control of the air supply pressure during the air supply and air replenishment operations, supplying air to the low-pressure tank with a stable output pressure, and avoiding the problem of overcharging the low-pressure tank. The set pressure value of the second pilot valve is set to be slightly higher than the target pressure of the low-pressure tank, and the speed of air supply and air replenishment is increased while controlling the output pressure of the pressure reducing valve.

[0052] When the first air pressure sensor detects that the pressure of the low-pressure tank has reached the target air pressure, a feedback signal is sent to the main control unit to control the switch solenoid valve to close, thereby completing the air supply and air replenishment to the low-pressure tank.

[0053] In order to increase the overall air replenishment rate of the air supply system, the set pressure value of the second pilot valve is set to be greater than the target pressure of the low-pressure tank. At the same time, since the set pressure value of the first pilot valve is greater than the set pressure value of the second pilot valve, the set pressure value of the first pilot valve will be much greater than the target pressure of the low-pressure tank.

[0054] When a cluster launcher launches a UAV, the launch interval is very short (about 2s) during the continuous launch process, so that the low-pressure tank needs to quickly switch between the inflation and deflation states. At this time, the switch solenoid valve also frequently switches between opening and closing. The frequent switching of the switch solenoid valve causes pressure fluctuations at the output and input ends of the pressure reducing valve.

[0055] In the air circuit control unit formed by the pilot valve and the pressure reducing valve, the action of the pressure reducing valve is controlled by the set pressure value of the pilot valve. When the pressure at the output end of the pressure reducing valve forms a pressure balance with the pressure at the output end of the pilot valve, the pressure reducing valve will be closed; when the pressure at the output end of the pressure reducing valve is less than the pressure at the output end of the pilot valve, the pressure reducing valve will be opened to realize the opening and closing control of the pressure reducing valve.

[0056] However, when the pressure fluctuation impact at the output end of the pressure reducing valve and the main pipeline is too large, the set pressure value of the pilot valve will gradually increase, which will cause the pressure at the output end of the pressure reducing valve to gradually increase, affecting the air replenishment accuracy.

[0057] The present invention adopts a method of connecting two-stage pilot valves in series and then connecting them in parallel with the main pipeline. When the pressure fluctuation impact of the main pipeline is too large, the pressure fluctuation impact received by the pipeline on the side of the pilot valve will also be too large. If only one pilot valve is used, the set pressure value of the pilot valve will gradually increase under the action of the pressure fluctuation impact. When two pilot valves are connected in series, the pressure fluctuation impact of the main pipeline will be concentrated on the first pilot valve, so that the first pilot valve can play a filtering role. At this time, the pressure setting value of the second pilot valve can be kept stable, the output pressure is stable, and the output pressure and stability of the pressure reducing valve can be controlled.

[0058] In some embodiments, a first exhaust safety valve 11 for pressure relief is provided on the low-pressure tank 2 to ensure the safety of the gas supply of the low-pressure tank.

[0059] In some embodiments, an integrated valve block 13 is provided on the main line 7, a first ball valve 14 is provided between the first inlet end of the integrated valve block 13 and the outlet end of the high-pressure tank 1, the outlet of the integrated valve block 13 is respectively connected to the inlet end of the first pilot valve 5 and the inlet front end of the pressure reducing valve 3, and a second pressure sensor 10 for detecting the air pressure of the high-pressure tank and a second exhaust safety valve 12 for pressure relief are provided on the integrated valve block 13.

[0060] The first ball valve 14 is set as a switch for air supply. Before launching, the first ball valve is opened to provide an air supply source for the air circuit. At the same time, the first ball valve can be closed during the storage or transportation of the system to avoid leakage of the high-pressure tank and the air supply system pipeline due to long-term pressure.

[0061] The integrated valve block is integrated with a plurality of interfaces, which are respectively connected to the second pressure sensor to detect the pressure in the high-pressure tank, and connected to the second exhaust safety valve to ensure the safety of the high-pressure tank.

[0062] In some embodiments, a quick-change connector 16 for connecting to the base station air source is provided at the second inlet end of the integrated valve block 13, and a second ball valve 15 is provided at the outlet end of the integrated valve block, and the second ball valve 15 is respectively connected to the inlet end of the first pilot valve 5 and the inlet front end of the pressure reducing valve 3.

[0063] The quick-change connector 16 and the second ball valve 15 are respectively connected to the interface of the integrated valve block, so that the high-pressure tank can be quickly inflated through the base station gas source 17. When inflating the high-pressure tank, close the second ball valve, open the first ball valve, connect the quick-connect connector to the base station gas source, and after the inflation is completed, disconnect the quick-change connector. The quick-change connector has the performance of self-sealing after disconnection. When the pressure in the high-pressure tank is overcharged, the second exhaust safety valve can be used to automatically exhaust and release the pressure to ensure the safety of the high-pressure gas circuit.

[0064] In some embodiments, a launch valve 19 is provided between the low-pressure tank 2 and each launch tube 18, and the launch valve 19 is connected to the main control unit 8. During launch, the main control unit controls the opening of the launch valve, and the low-pressure tank supplies air into the launch tube to complete the launch of the UAV in the current launch tube.

[0065] On the other hand, based on the above-mentioned UAV pneumatic ejection air supply system, the present invention also provides an air supply control method for UAV pneumatic ejection, so as to realize fast and accurate air replenishment of the low-pressure tank during the continuous launch of the UAV.

[0066] In some embodiments, the air supply control method for pneumatic ejection of a drone includes:

[0067] The set pressure values ​​of the first pilot valve and the second pilot valve are set so that the set pressure value of the first pilot valve is greater than the air pressure required by the low-pressure tank, and the set pressure value of the second pilot valve is greater than the air pressure required by the low-pressure tank and less than the set pressure value of the first pilot valve, and the output pressure of the pressure reducing valve is controlled by the pressure output by the second pilot valve;

[0068] The main control unit controls the switch of the switch solenoid valve according to the pressure data obtained from the first pressure sensor. When the pressure data of the first pressure sensor reaches the target air pressure required by the low-pressure tank, the main control unit controls the switch solenoid valve to close.

[0069] When the air pressure in the low-pressure tank reaches the target pressure, the main control unit controls the launch valve of one of the launch tubes to be launched to open, completing the launch of a UAV;

[0070] After completing the launch of a drone, the air pressure in the low-pressure tank decreases, and it is necessary to replenish air in the low-pressure tank before the next launch. At this time, the main control unit controls the switch solenoid valve to open and replenish air in the low-pressure tank until the target air pressure is reached;

[0071] Cycle in sequence to complete the firing of each launch tube.

[0072] Reference Figure 1 The UAV pneumatic catapult air supply system shown in the figure has 25 UAV launch units clustered in 5 rows and 5 columns connected to the low-pressure tank. Each launch unit includes a launch valve and a launch tube. The main control unit controls the automatic air replenishment operation and the launch valve to achieve continuous launch control of the 25 UAV launch units. No human operation or intervention is required during the launch process, and the degree of automation is high.

[0073] When supplying and replenishing air to the low-pressure tank, due to the pressure fluctuation inside the low-pressure tank, in order to avoid the switch solenoid valve from frequently operating after receiving the pressure feedback signal and affecting the speed of inflation and replenishment, a gas supply buffer room can be set, and the switch solenoid valve can be controlled based on the gas supply buffer room.

[0074] Generally, the minimum value of the air supply buffer zone is not less than the minimum value of the target air pressure control accuracy range and the maximum value of the air supply buffer zone is greater than the maximum value of the target air pressure control accuracy range. For example, when the target air pressure value of the low-pressure tank is 7.55±0.05bar, the air supply buffer zone can be set to 7.5~7.8bar.

[0075] When the low-pressure tank is inflated for the first time, since there is no gas in the low-pressure tank before launch, the inflation time required for the first inflation is relatively long. Therefore, during the launch operation, when the switch solenoid valve is powered on in the main control unit or the launch control system is bound, a control instruction is issued to the switch solenoid valve in advance to control the switch solenoid valve to open and inflate the low-pressure tank in advance, so as to complete the first inflation of the low-pressure tank in the launch preparation stage. When the main control unit receives the launch control instruction, it controls the launch valve to open, and the UAV can be launched quickly.

[0076] The present invention adopts a two-stage pilot valve, a pressure reducing valve and a switch solenoid valve to form an air supply control system, which has significant advantages in achieving the air replenishment control accuracy of the low-pressure tank compared to the control method using only one pilot valve and a pressure reducing valve.

[0077] When a pilot valve is used for air supply control, the pilot valve and the pressure reducing valve form a pressure balance circuit. By setting the set pressure value of the pilot valve, the pressure is transmitted to the pressure reducing valve through pressure to control the pressure output of the pressure reducing valve. This control method will cause rapid fluctuations in the pressure at the output end of the pressure reducing valve during continuous air supply and air replenishment operations during continuous launch, forming pressure pulses, causing pressure fluctuations in the pilot valve pipeline. The originally set set pressure value of the pilot valve changes and gradually increases, causing the pressure at the output end of the pressure reducing valve to gradually increase, and the air replenishment pressure in the low-pressure tank will also gradually increase with the number of air replenishment operations, making it difficult to achieve accurate air replenishment.

[0078] As mentioned above, when only one pilot valve is used, when 25 rounds are fired continuously, the pressure setting value of the pilot valve and the pressure at the output end of the pressure reducing valve will increase by about 2 bar. Therefore, when the 25th round is fired, even if the switch solenoid valve is set for pressure feedback control, it will be difficult to achieve accurate control of the inflation pressure through pressure feedback control due to the pressure difference of about 2 bar between the main line and the low-pressure tank, resulting in overcharging of the low-pressure tank. As the number of firings increases, the impact on control accuracy will also increase.

[0079] This control method, when performing air replenishment operations during continuous UAV launches, will cause the actual value of the inflation pressure in the low-pressure tank to gradually increase starting from the first shot. The air pressure provided for each UAV launch is different, resulting in inconsistent UAV launch speeds, affecting the UAV launch control accuracy.

[0080] The present invention adopts a combined control method of a two-stage pilot valve, a pressure reducing valve and a switch solenoid valve. The first pilot valve is used for filtering to reduce the influence of pressure fluctuations on the set pressure value of the second pilot valve. The second pilot valve is used to control the output pressure of the pressure reducing valve. The problem of the change of the set pressure value of the second pilot valve is well solved through the cooperation between the two-stage pilot valves; through the two-stage voltage stabilization control, the output pressure of the pressure reducing valve can always be maintained in a constant range, thereby realizing precise control of the gas replenishment pressure in the low-pressure tank.

[0081] Based on the above-mentioned control of the output pressure of the pressure reducing valve, the pressure drop at the input end of the switch solenoid valve is reduced and the pressure is stable, so that the air replenishment accuracy can be controlled while realizing automatic air replenishment, so that the air pressure in the low-pressure tank can be maintained within the target pressure range during each launch, ensuring the control accuracy of continuous launch of the UAV.

[0082] Reference Figure 2 , which is a pressure curve diagram of the gas supply operation for the low-pressure tank using the gas supply control system and the gas supply control method of the present invention during the continuous launch process.

[0083] As can be seen from the figure, when the air supply system is used to supply and replenish air for 25 groups of launching units for continuous launching, from the first shot to the last shot, the pressure value in the low-pressure tank after each air replenishment is basically the same, indicating that the air supply system of the present invention has good inflation pressure control accuracy, and the time required for air replenishment between each shot is very short.

[0084] Moreover, based on the comparison of the two rounds of tests, it can be seen that in the two rounds of continuous launch operations, the gas supply pressure curves basically overlap, indicating that the gas supply system has good stability and reliability and can meet the needs of repeated launches of cluster launch devices.

[0085] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. used to indicate the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship commonly placed when the product of the invention is used. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0086] In addition, if the terms "horizontal" or "vertical" appear in the description of the present invention, it does not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0087] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood in combination with specific circumstances.

[0088] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent change made to the above embodiment based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. UAV pneumatic ejection air supply system, characterized in that: include: The high-pressure tank is used to supply gas to the low-pressure tank, and the gas pressure in the high-pressure tank is greater than the gas pressure in the low-pressure tank; A low-pressure tank, which is connected to a plurality of launch tubes and is used to provide an air source required for pneumatic ejection of the drone. The low-pressure tank is connected to the high-pressure tank through a main pipeline, and a first pressure sensor for detecting the air pressure of the low-pressure tank is provided on the low-pressure tank; A first gas circuit control unit, comprising a pressure reducing valve and a switch solenoid valve arranged on the main pipe, wherein the front end of the inlet of the pressure reducing valve is connected to the high-pressure tank, the outlet end of the pressure reducing valve is connected to the switch solenoid valve, and the switch solenoid valve is connected to the low-pressure tank; A second gas circuit control unit comprises a first pilot valve and a second pilot valve connected in series, wherein the inlet end of the first pilot valve is respectively connected to the inlet front end of the high-pressure tank and the pressure reducing valve, and the outlet end of the second pilot valve is connected to the pressure reducing valve. The set pressure value of the first pilot valve is greater than the target air pressure of the low-pressure tank, the set pressure value of the second pilot valve is not less than the target air pressure of the low-pressure tank and less than the set pressure value of the first pilot valve, and the output pressure of the pressure reducing valve is controlled by the pressure output by the second pilot valve; the set pressure value of the first pilot valve is 2.5-3 times the target air pressure of the low-pressure tank, and the set pressure value of the second pilot valve is 1.5-2 times the target air pressure of the low-pressure tank; A main control unit is connected to the first pressure sensor and the switch solenoid valve respectively, and is used to control the switch solenoid valve on and off according to the pressure data obtained from the first pressure sensor. When the pressure data of the first pressure sensor reaches the target air pressure required by the low-pressure tank, the main control unit controls the switch solenoid valve to close.

2. The air supply system for the pneumatic ejection of a UAV according to claim 1, characterized in that: The low-pressure tank is provided with a first exhaust safety valve for pressure relief.

3. The air supply system for the pneumatic ejection of a drone according to claim 1, characterized in that: An integrated valve block is arranged on the main pipe, a first ball valve is arranged between the first inlet end of the integrated valve block and the outlet end of the high-pressure tank, the outlet of the integrated valve block is respectively connected to the inlet end of the first pilot valve and the inlet front end of the pressure reducing valve, and a second pressure sensor for detecting the air pressure of the high-pressure tank and a second exhaust safety valve for pressure relief are arranged on the integrated valve block.

4. The air supply system for the pneumatic ejection of a UAV according to claim 3 is characterized in that: The second inlet end of the integrated valve block is provided with a quick-change connector for connecting to the base station air source, and the outlet end of the integrated valve block is connected to the second ball valve, which is respectively connected to the inlet end of the first pilot valve and the inlet front end of the pressure reducing valve.

5. The air supply system for the pneumatic ejection of a UAV according to claim 1, characterized in that: A launching valve is respectively arranged between the low-pressure tank and each launching tube, and the launching valve is connected to the main control unit.

6. The air supply control method of the air ejection air supply system of the unmanned aerial vehicle according to any one of claims 1 to 5, characterized in that: include: The set pressure values ​​of the first pilot valve and the second pilot valve are set so that the set pressure value of the first pilot valve is greater than the air pressure required by the low-pressure tank, and the set pressure value of the second pilot valve is greater than the air pressure required by the low-pressure tank and less than the set pressure value of the first pilot valve, and the output pressure of the pressure reducing valve is controlled by the pressure output by the second pilot valve; The main control unit controls the switch of the switch solenoid valve according to the pressure data obtained from the first pressure sensor. When the pressure data of the first pressure sensor reaches the target air pressure required by the low-pressure tank, the main control unit controls the switch solenoid valve to close.

7. The gas supply control method according to claim 6, characterized in that: The air supply buffer zone is set, the minimum value of the air supply buffer zone is not less than the minimum value of the target air pressure value control accuracy range and the maximum value of the air supply buffer zone is greater than the maximum value of the target air pressure value control accuracy range; When the pressure data detected by the first pressure sensor is within the air supply compensation buffer zone, the main control unit controls the switch solenoid valve to close.

8. The gas supply control method according to claim 6, characterized in that: When the air pressure in the low-pressure tank reaches the target air pressure, the main control unit controls the launch valve of one of the launch tubes to be launched to open; After completing the launch of a UAV, the main control unit controls the replenishment of air to the low-pressure tank until the target air pressure is reached, and the cycle is repeated in sequence to complete the launch of each launch tube.

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